CN101405918B - Fastening system for fastening a cabin fitting element to a support structure of an aircraft - Google Patents
Fastening system for fastening a cabin fitting element to a support structure of an aircraft Download PDFInfo
- Publication number
- CN101405918B CN101405918B CN2007800095781A CN200780009578A CN101405918B CN 101405918 B CN101405918 B CN 101405918B CN 2007800095781 A CN2007800095781 A CN 2007800095781A CN 200780009578 A CN200780009578 A CN 200780009578A CN 101405918 B CN101405918 B CN 101405918B
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- China
- Prior art keywords
- plug
- fixed support
- bushing
- fastening system
- bushing device
- Prior art date
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- Expired - Fee Related
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
- H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
- H01R13/629—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances
- H01R13/631—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for engagement only
- H01R13/6315—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for engagement only allowing relative movement between coupling parts, e.g. floating connection
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- Installation Of Indoor Wiring (AREA)
- Details Of Connecting Devices For Male And Female Coupling (AREA)
Abstract
The invention relates to a fastening system for fastening a cabin fitting element (1) with at least one electrical installation on a support structure (2) of an aircraft. During installation into the support structure (2), the cabin fitting element (1) is fixed in succession by at least one loose bearing (13) in at least one degree of translational freedom and then by at least one fixed bearing (3) in the at least one further degree of translational freedom. In order to ensure an improved installation and dismantling of cabin covering panels with electrical installation and to reduce the weight due to the components and also the installation space which is required, according to the invention a contact device with a bush arrangement (17, 21) and a plug arrangement (18, 23) is integrated in the at least one loose bearing (13) and/or the at least one fixed bearing (3), by which an electrical connection is produced between the support structure (2) and the electrical installation of the cabin fitting element (2) on fixing at least of one degree of translational freedom.
Description
Technical field
The present invention relates to a kind of according to claim 1 preamble be used for cabin fitting element is fastened to the fastening system on the supporting construction of aircraft.Particularly, but not exclusively, the present invention relates to have the cabin fitting element of at least one electric equipment (electrical installation).
Background technology
The liner of aircraft (lining) is made up of independent member usually, and wherein a large amount of plate (plate) or lath (panel) are arranged in the specific framework or supporting construction located adjacent one anotherly.These plates are for example as overhead guard or side cover.In maintenance work; For example for can be (promptly in the back of plate; Between the exterior skin and liner of aircraft) carry out maintenance work, must easily these cladding plates be taken off separately once more, and must be able to have no difficulty ground subsequently these plates are inserted once more.For the lath that is combined with electric device, this means and have to open and close once more lath each other or the mechanical connection between lath and the supporting construction and being electrically connected.In the current cabin Assembly part of having mentioned, be provided with mechanical fastener and electrical connector separately for this reason.Therefore, for example, the roof lath fixes through three or four machanical fasteners, and wherein two securing members are configured to not fixed support (loose bearing) and another one or two securing members are configured to fixed support.The electrical connection of this roof lath connects realization through plug type usually, and one of them connector is fixedly mounted on the lath, and a connector is not fixedly mounted on the supporting construction of aircraft.
Low and therefore avoid with lath damage to being electrically connected when its supporting construction is unclamped and take off for the mechanical stress that keeps plug to connect; Safety cable (check cable) must be set in the prior art in addition; The lath that this safety cable will unclamp from its grappling (anchoring) remains in suspension status, up to irrespectively realizing or separate plug being connected with the mechanical anchor of two parts.Therefore, in opposite operation, promptly when lath was installed, safety cable also helped this operation.
Put down carrying out attaching/detaching in the process of lath (length that depends on safety cable), in order to ensure suitable play (play), cable of the prior art must be installed with the mode with unnecessary length.The result who does like this is exactly that to have to use only be the required material of assembling.Therefore, unnecessarily increased the weight of aircraft.In addition, long cable is not fixed, and they can along with the motion of aircraft with not controlled way motion, this possibly cause noise and cause through the damage of friction to cable.
Summary of the invention
The objective of the invention is to guarantee to improve the installation and removal of cabin cladding plate, and reduce the weight that causes owing to part, and reduce required installing space with electric accessory.
This purpose realizes through the fastening system according to claim 1.The preferred embodiments of the present invention are themes of dependent claims.
The present invention is based on following design; Promptly; Required electrically contacting is attached at least one mechanical bearings,, between supporting construction and installed part, forms and have being electrically connected of a plurality of contacts so that in joining not fixed support to or join in the process in the fixed support.
According to fastening system of the present invention, that be used for the cabin fitting element with at least one electric equipment is fastened to the supporting construction of aircraft; Wherein, Be installed in the supporting construction cabin fitting element in succession through at least one not fixed support fixing at least one translation freedoms and fixing on another translation freedoms at least through at least one fixed support subsequently; It is characterized in that; Contact device (device) with lining (bush) device and plug-in device is incorporated at least one not in the fixed support and/or at least one fixed support; Thus, in the fixation procedure of at least one translation freedoms, between the electric equipment of supporting construction and cabin fitting element, form and be electrically connected.
Particularly, the preferred embodiments of the present invention have one or more following characteristics (these characteristics are that be fit to and feasible) with regard to technical elements:
Bushing device and/or plug-in device can be around at least one axis rotations perpendicular to direction of insertion in supporting member;
Bushing device and/or plug-in device can move between first stop part and second stop part of connector direction in supporting member;
In the fixation procedure of translation freedoms, bushing device and plug-in device are relative to each other aimed at through the guide finger that sharply attenuates of coning tapered guide openings and complementation automatically;
In the fixation procedure of translation freedoms, bushing device and plug-in device are relative to each other aimed at through complementary roughly coning tapered profile automatically;
Fixed support comprises connecting pin and access portal, and bushing device and plug-in device are arranged in this connecting pin and access portal respectively symmetrically, so that when this fixed support of assembling, bushing device forms with plug-in device and is electrically connected;
Bushing device and/or plug-in device can rotate around its symmetry axis, and are provided with the aligning auxiliary member, and when two and half ones of supporting member were relative to each other guided, bushing device was aimed at auxiliary member with plug-in device through this and relative to each other aimed at automatically;
, bushing device and plug-in device produce visible signal and/or audible signal when being connected with each other;
One mechanical braking mechanism is set, so that bushing device is connected with the permanent of plug-in device;
One magnetic closed-system is set, so that bushing device is connected with the permanent of plug-in device.
Therefore, the present invention especially has the following advantages, that is, for mounted lath, the cable guide of qualification is fixed, thereby has avoided the motion of cable, because the unnecessary length of cable no longer is essential for installation.
Description of drawings
With reference to the accompanying drawing description of preferred embodiments, other advantages of the present invention and characteristic will be obvious from following.
Fig. 1 shows according to the lath of prior art and has the independently mechanical connection of the strutting piece of Electical connector.
Fig. 2 A and Fig. 2 B show the embodiment according to securing supports of the present invention, and the Electical connector that is wherein combined is in released state and assembled state.
Fig. 3 shows the element according to the embodiment of fixed support of the present invention according to Fig. 2 with vertical view.
Fig. 4 show according to of the present invention, be used for the not embodiment of the Electical connector of fixed support.
Fig. 5 show according to of the present invention, be used for the not another embodiment of the Electical connector of fixed support.
Fig. 6 shows the embodiment according to fixed support of the present invention that is in assembled state according to Fig. 5.
Embodiment
Part as the lath 1 of cabin fitting element has been shown, supporting construction 2 mechanical connections of this part and aircraft and being electrically connected among Fig. 1.Usually, these laths are connected with the respective support structure of aircraft with one or more fixed support through one or more not fixed support.Fixed support limits the position of lath in supporting construction, that is, the position in aircraft, the mechanical tolerance that meanwhile for example causes by the fluctuation of temperature or by vibration and the dynamic change of position can balance through fixed support not.For at installation and removal supporting slat all in final fastening process, installed part (intermediate mounting) in the middle of being provided with in addition.Although come meeting stile and supporting construction through fixed support not, this lath is limited at least one translation freedoms.In second stage, lath only is fixed with respect to other degrees of freedom.The fastening possibility of further aiming at lath with respect to other translation freedoms that provides in two stages; The possibility of carrying out further attended operation especially also is provided; Such as forming such electrically contacting; That is, after finally being fastened on lath on the supporting construction, because this moment, some element no longer can electrically contact near these that just no longer can carry out.
Lath according to Fig. 1 keeps through the not fixed support with erecting device and anchoring device on a side.Further describe this not fixed support below.On opposite side, through fixed support 3 lath is limited in its final position on the supporting construction 2 of aircraft.Comprise that according to the fixed support 3 of prior art the access portal 5 that is positioned at the connecting pin 4 with latch recess or locking groove 4a on lath 1 one sides and is positioned on supporting construction 2 one sides presss from both sides 5a with being connected.When connecting fixed support 3, connect folder 5a and join among the locking groove 4a on the support-side, and therefore lath 1 is fixed on the supporting construction 2.
Before closing fixed support 3 and lath 1 being fixed in its final position on the supporting construction 2; Lath 1 loosely is remained on the supporting construction 2 of aircraft through safety cable 6; So that still there is intermediate space, be connected thereby can between lath 1 and supporting construction 2, form plug.Safety cable 6 is connected with supporting construction 2 through connector 7, and is connected with lath 1 through connector 8.The connector 7 of safety cable 6 and 8 can be nonvolatil, perhaps can according to circumstances form.
The cable 10 that lath 1 is connected through safety cable 6 and supporting construction 2 temporary on the cable 9 that allows on the support-side and the panel side is electrically connected through contacting with 12 connector with two elements 11.Like this, shown in prior art in, connector contact 12 be positioned at support-side on and the cable 9 that dangles from supporting construction 2 looselys be connected, cable 9 is very long so that exist sufficient play to install being used for.On the other hand, the connector contact on the panel side 11 is permanently connected with lath 1.Therefore, connector contact 12 is inserted in the connector contact 11 perhaps from wherein taking out, as shown by double-head arrow.Therefore, through fixed support security strip 1 not with fix between these laths through fixed support 3, contact 12 can be connected with contact 11.Fixed support 3 is engaged subsequently, and lath is in its final position, and electrically contacts and connected.It is obvious to the skilled person that on the one hand, the cable of fixed connection and loose cable are equal, and on the other hand, supporting construction and cabin fitting element also can be chosen to embodiment shown here in different.
As noted above, lath 1 keeps through fixed support not 13 on a side, through fixed support 3 final security strips before this lath be suspended in this not in the fixed support.Fixed support 13 does not comprise erecting device 14 and anchoring device 15.Erecting device 14 is positioned on the side of supporting construction 2 and comprises the infundibulate device substantially, and this infundibulate device can have the shape of truncated cone or truncated pyramid, and wherein its A/F can be different with opening angle for each direction.Anchoring device 15 is arranged on the side of lath 1 and comprises the reinforcement (thickening) that is pressed into erecting device 14 substantially.Be clear that very that to those skilled in the art on the one hand, erecting device 14 is equal, and on the other hand, anchoring device 15 also can be chosen to embodiment shown here in different.
Fixed support 13 is not only fixed one or two translation freedoms.In Fig. 1, through securing supports not fixed make progress among Fig. 1 and perpendicular to the translation freedoms of this plan.This points out through the straight double-head arrow on the fixed support 13 not in Fig. 1.The dextrosinistral degree of freedom is only fixing through fixed support 3 among Fig. 1.Rotatablely moving can be irrelevant with translation freedoms; This double-head arrow through bending in Fig. 1 is pointed out.
Two different working steps of the fastening needs of prior art middle plate strip promptly, are the mechanical fasteners of lath and supporting construction on the one hand, are lath on the other hand and being electrically connected of mechanical structure.In addition, need to adopt the intermediate connector of safety cable 6 forms.
On the other hand, produced not fixed support or the fixed support that is combined with contact device according to the present invention.With reference to Fig. 2 to Fig. 6 this is made an explanation below.
In Fig. 2 A and Fig. 2 B, embodiments of the invention have been shown, wherein contact is incorporated in the fixed support.According to the fixed support 16 of Fig. 2 A and Fig. 2 B have with according to Fig. 1 as the mechanically identical structure of fixed support 3 shown in the instance of prior art.Yet; Different with prior art is that in fixed support 16 according to the present invention, the center that faces toward the access portal 5 that is used for connecting pin 4 is installed in supporting construction 2 sides with bushing device 17; Particularly, said bushing device 17 is arranged with respect to access portal 5 symmetrically.Shown in embodiments of the invention in, bushing device 17 has a series of independent lining 19 on supporting construction 2.
Complementary plug-in device 18 is positioned on the side of cabin fitting element to be installed 1, and this plug-in device is provided with independent connector 20, this connector again with independent lining 19 complementations.Likewise, plug-in device 18 is arranged with respect to connecting pin 4 symmetrically.Cable 10 leads to supply or data processing unit (undeclared) from the bushing device 17 on supporting construction 2 sides.The cable 9 that will be used for the supply of electric equipment (not shown) through the plug-in device 18 on the side of lath 1 is installed in lath 1; Particularly; Said cable is connected with lath through cable clip 9a securely; Thereby it can not arrived in the process of assembling fixed support 16 between two supporting half ones, and in flight course, can not carry out not controlled moving.
In Fig. 2 A, show the fixed support that is in released state.When this supporting member is assembled, have the access portal 5 that the connecting pin 4 that connects groove 4a passes supporting construction 2 and insert, and with is connected folder 5a and locks.In Fig. 2 B, show the fixed support that is in assembled state.Shown in figure, in the assembling process of fixed support 16, formation automatically is electrically connected between lath 1 and the supporting construction 2.When upwards moving lath 1 to supporting construction, pin 20 joins in the lining 19, and therefore guarantees electrically contacting between cable 9 and the cable 10 on the supporting construction 2 on the lath 1.Aim at the correct of plug-in device 18 in order to ensure bushing device 17, at least one in two contact devices 17,18 can center on its symmetry axis (that is, connecting pin 4 or access portal 5) rotation.For this reason, the aligning auxiliary member (not shown) of buckle (bayonet) or the sealed form of spiral can be set, thereby when half one of will supporting gathers together, make two contact devices 17,18 itself relative to each other automatically aim at.
In Fig. 3, show bushing device 17 with vertical view with independent lining 19.As can be seen from Figure 3, the distribution of the independent lining in the contact device 17 is arbitrarily basically, and can select to have the intensive cover layer or the more not intensive cover layer of independent lining as required.Yet as directed, this distribution is symmetrical with respect to access portal 5, so that the interim aligning of two contact devices 17,18 is simple and is easy to realize, and when contact device moves towards each other, forms contact.
Can directly find out, can in single job step, realize the assembling of supporting member and the formation that electrically contacts this means the time of having saved aircraft manufacturing and maintenance thereof.In addition, saved middle installed part (it only is that installation is required), thereby can save extra weight through fastening system according to the present invention such as safety cable.
The alternative embodiment that is combined with the fastening system of contact device according to of the present invention has been shown in Fig. 4.Fig. 4 shows according to bushing device 21 of the present invention, and this bushing device has and is used for the not independent lining 19 of the erecting device 14 of fixed support.In an illustrated embodiment, erecting device 14 has specific cross section in its porch, and this cross section reduces along with the increase of the degree of depth.The direction of insertion of plug part (not shown) is pointed out through " z " in Fig. 4.Because erecting device 14 is at the big cross section of porch, the plug part (not shown) has certain play along " x " and " y " direction (that is, perpendicular to connector direction " z ").Along with the insertion depth increase of plug part (not shown), its play reduces, thereby the final edge of plug part " x " and " y " direction is fixed and only has the degree of freedom along " z " direction.This points out through the cone around direction of insertion " z " in Fig. 4.In order to improve the sliding properties of plug part (not shown), erecting device 14 comprises the alignment springs 22 at least two sides that are arranged on erecting device 14.As directed, this alignment springs 22 can be along straight-line extension, and likewise, and it also can be by slight curving so that its alignment result according to the degree of depth that penetrates stronger with more a little less than.In this embodiment, plug part keeps through alignment springs 22 and is positioned in the center between its two side elements.At this,, other alignment springs also can be set, for example the above and below in erecting device 14 except the only left side in erecting device 14 and the right are provided with an alignment springs 22.
Replacedly, the centering of bushing device and plug-in device and aligning can also carry out through centre pilot pin and centre pilot opening.With reference to Fig. 5 and Fig. 6 the such embodiment of the present invention is described below.
Corresponding bushing device 21 with independent lining 19 and the plug-in device 23 with independent connector 20 have been shown in Fig. 5.Bushing device 21 has guide openings 24, and preferably, this guide openings is positioned at the center.Corresponding guide finger 25 on plug-in device 23 sides joins in this guide openings 24, thereby makes the connector 20 of plug-in device 23 correspondingly aim at the lining 19 of bushing device 21.Preferably, guide finger 25 is longer than the independent connector 20 of reality substantially, so that this guide finger arrived guide openings 24 before an independent connector 20 arrives an independent lining 19.By this way, prevented that independent lining 19 and independent connector 20 from bearing mechanical stress.Plug-in device 23 is pointed out through the double-head arrow of intersection and the symmetry axis of dotted line with respect to the initial play of bushing device 21.
In order to enlarge the angle that two contact devices 21 and 23 can move towards each other, guide finger 25 is configured as taper shape at its most advanced and sophisticated place, so that guide finger also can be incorporated in the guide openings 24 of contact device 21 at disadvantageous angle place.Along with two contact devices continue near moving each other, independent contact 19 and 20 itself is relative to each other automatically aimed at.
As mentioned that contact device 21 for example is arranged in the erecting device 14 of fixed support not.In a similar fashion, 23 of contact devices are arranged in the anchoring device 15.In a preferred embodiment of the invention, at least one in the contact device 21,23 can be rotated perpendicular to direction of insertion " z ".Especially preferably, contact device can be around two axis rotations perpendicular to direction of insertion.At this, the maximum anglec of rotation can and depend on the prealignment that contact device carries out through mechanical bearings haply up to 90 °.Therefore, contact is irrelevant with mechanical bearings to a certain extent, and is forming certain mobility of having guaranteed contact device when being electrically connected.
The not fixed support that is combined with contact device 21 and 23 that is in assembled state has been shown in Fig. 6.At this, fixed support 13 does not comprise erecting device 14 that is combined with two plug-in devices 23 and the anchoring device 15 that is combined with two bushing devices 21.The anchoring device 15 that is combined with two bushing devices 21 is introduced in the erecting device 14 that is combined with two plug-in devices 23.When formation electrically contacted, guide finger 25 made that with guide openings 24 two devices 21,23 are aligned with each other.Contact device 21 links to each other with cable 26 respectively on their rear side with corresponding contact device 23, and wherein in an illustrated embodiment, the cable 26a, 26b, 26c and the 26d that are used for contact device 21 and 23 comprise four independent lead-in wires respectively.Other lead-in wires that certainly, can envision equally on the contact distribute.
The play of the not fixed support shown in Fig. 5 limits according to the length that is mounted 14 region covered of device of anchoring device 15, and said play is pointed out through the double-head arrow of two bendings.
In embodiments of the invention shown in Fig. 6, plug-in device 23 is disposed in the erecting device 14 and between two stop part 27a and 27b.These stop parts 27a, 27b limit plug-in device 23 and can put into zone wherein.Therefore, in the assembling process of supporting member 13, plug-in device 23 is pressed backward, and when further not retreating and if only if plug-in device is stoped by back stop part 27a, independent connector 20 just penetrates in the independent lining 19 and forms reliable electrical contact.Vice versa, and when loosening supporting member 13, plug-in device 23 is along with bushing device 21 also is moved further a segment distance, and when further not following and if only if plug-in device is stoped by preceding stop part 27b, independent connector 20 is just pulled out from independent lining 19.Through this " hysteresis " in the installation and removal process, realized that feasible electrical connection is really reliable, and for example under the situation that occurs vibrating owing to flight operation, can not become disconnection.
Yet the invention is not restricted to the embodiments described.In the preferred embodiments of the present invention (this embodiment is not shown), mechanical caging and the formation that particularly electrically contacts are pointed out through optical signal or audible signal.Therefore, the indication piece of plastics can stretch out from the opening in opening the lath 1 or the supporting construction 2, and this indication piece only contacting between lath 1 and supporting construction 2 just becomes visible when as illustrated, forming.This can realize that this joint that can hear can further amplify through snapping in of extra Plastic tongue is next through the joint that can hear.This Plastic tongue is so shaped that preferably they form little, surmountable resistance in the process of the locking and unlocking.Replacedly, except being used for audible signal, this Plastic tongue can also be used as mechanical braking mechanism, this mechanism is set so that the permanent connection of contact device.Other auxiliary member also can be used for firm connection, such as the magnetic closed-system of the permanent connection that is used for contact device.
It is obvious to the skilled person that in described embodiment, electric components connector and lining can exchange equally, and mechanical component erecting device and anchoring device can exchange also, only if this situation is got rid of clearly.
Reference number
1 cabin fitting element
2 supporting constructions
3 fixed support
4 connecting pin 4a lock groove
5 access portal 5a connect folder
6 safety cables
First anchor log of 7 safety cables
Second anchor log of 8 safety cables
Cable on 10 support-side
Connector contact on 11 structure side
(unfixing) connector contact on 12 support-side
13 fixed support not
14 not fixed support, erecting devices
15 not fixed support, anchoring devices
16 have the not fixed support of contact device
17 are used for fixing the bushing device of supporting member
18 are used for fixing the plug-in device of supporting member
19 independent linings, the guide of hollow
20 independent connector, pins
21 are used for the not bushing device of fixed support
22 alignment springs
23 are used for the not plug-in device of fixed support
24 are used for the not guide openings of the bushing device of fixed support
25 guide fingers
26 wire harness, 26a-26d
27 brake components, 27a detent rear, 27b detent front
X, y, z translation freedoms.
Claims (9)
1. one kind is used for the cabin fitting element with at least one electric equipment (1) is fastened to the fastening system on the supporting construction (2) of aircraft; Wherein, Be installed in the said supporting construction (2) said cabin fitting element (1) in succession through at least one not fixed support (13) fixing at least one translation freedoms and fixing on another translation freedoms at least through at least one fixed support (3) subsequently; It is characterized in that
Contact device with bushing device (17,21) and plug-in device (18,23) be incorporated into said at least one not in the fixed support (13); Thus in the process of fixing at least one translation freedoms; Between the electric equipment of said supporting construction (2) and said cabin fitting element (1), form and be electrically connected, and said bushing device and/or said plug-in device can move between first stop part and second stop part of direction of insertion in said not fixed support.
2. fastening system according to claim 1 is characterized in that,
Said bushing device (17,21) and/or said plug-in device (18,23) can be around rotating perpendicular at least one upright axis of direction of insertion (x, y) in said not fixed support (13).
3. fastening system according to claim 2 is characterized in that,
When fixing a translation freedoms, said bushing device (21) is relative to each other aimed at through the guide finger that sharply attenuates (25) of coning tapered guide openings (24) and complementation with said plug-in device (23) automatically.
4. fastening system according to claim 2 is characterized in that,
When fixing a translation freedoms, said bushing device (21) is relative to each other aimed at through complementary roughly coning tapered profile with said plug-in device (23) automatically.
5. fastening system according to claim 1 is characterized in that,
Said fixed support (3) comprises connecting pin (4,4a) and access portal (5,5a); Bushing device (17) and plug-in device (18) are arranged about said connecting pin and said access portal respectively symmetrically; Thereby when the said fixed support of assembling (3), be electrically connected with said plug-in device (18) formation at said bushing device (17).
6. fastening system according to claim 5 is characterized in that,
Said bushing device (17) and/or said plug-in device (18) can be around its axis of symmetry rotations; And be provided with the aligning auxiliary member; When two and half ones of said fixed support were close to each other, said bushing device (17) was relative to each other aimed at through the said auxiliary member of aiming at said plug-in device (18) automatically.
7. according to each described fastening system in the aforementioned claim, it is characterized in that,
When said bushing device (17) and said plug-in device (18) produce visible signal and/or audible signal when being connected with each other.
8. fastening system according to claim 1 is characterized in that,
One mechanical braking mechanism is set, so that permanent connection of said bushing device (17) and said plug-in device (18).
9. fastening system according to claim 1 is characterized in that,
One magnetic closed-system is set, so that permanent connection of said bushing device (17) and said plug-in device (18).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102006012730A DE102006012730B3 (en) | 2006-03-17 | 2006-03-17 | An attachment system for attaching a cabin trim element to a support structure of an aircraft |
| DE102006012730.7 | 2006-03-17 | ||
| PCT/EP2007/052500 WO2007107511A1 (en) | 2006-03-17 | 2007-03-16 | Fastening system for fastening a cabin fitting element to a support structure of an aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101405918A CN101405918A (en) | 2009-04-08 |
| CN101405918B true CN101405918B (en) | 2012-08-15 |
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ID=38050187
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2007800095781A Expired - Fee Related CN101405918B (en) | 2006-03-17 | 2007-03-16 | Fastening system for fastening a cabin fitting element to a support structure of an aircraft |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US8167624B2 (en) |
| EP (1) | EP2005533B8 (en) |
| JP (1) | JP2009530150A (en) |
| CN (1) | CN101405918B (en) |
| BR (1) | BRPI0708845A2 (en) |
| CA (1) | CA2644159A1 (en) |
| DE (1) | DE102006012730B3 (en) |
| RU (1) | RU2432651C2 (en) |
| WO (1) | WO2007107511A1 (en) |
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| WO2016112014A1 (en) * | 2015-01-05 | 2016-07-14 | Mizco International Inc. | Alignment apparatus and a method for manufacturng thereof |
| EP3514436B1 (en) * | 2018-01-17 | 2019-12-11 | Axis AB | A fastening arrangement, a fastening arrangement kit and use of a fastening arrangement kit |
| EP3949027A4 (en) * | 2019-04-03 | 2022-11-16 | Microsoft Technology Licensing, LLC | Tethered connector assembly |
| DE102019132105A1 (en) * | 2019-11-27 | 2021-05-27 | Lubas Maschinen Gmbh | Contacting device |
| EP3849028A1 (en) * | 2020-01-09 | 2021-07-14 | Rosenberger Hochfrequenztechnik GmbH & Co. KG | Connector assembly and electrical connector |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1527854A (en) | 1967-03-01 | 1968-06-07 | Commissariat Energie Atomique | Connector with automatic plug-in of co-operating elements |
| US3810258A (en) * | 1972-07-11 | 1974-05-07 | W Mathauser | Quick connect electrical coupler |
| US3951500A (en) * | 1974-06-10 | 1976-04-20 | Bunker Ramo Corporation | Circular rack and panel connector |
| US4289368A (en) * | 1979-08-31 | 1981-09-15 | The Bendix Corporation | Full mate indicator for detachable connectors |
| DE3536142A1 (en) * | 1985-10-10 | 1987-04-16 | Opel Adam Ag | Multipole electrical connection, which is constructed as a plug connection, between two components which are connected to one another in an articulated manner, especially between the bodywork and side door of motor vehicles |
| DE8530786U1 (en) | 1985-10-30 | 1989-02-16 | Siemens AG, 1000 Berlin und 8000 München | Catching device |
| US4950174A (en) * | 1989-02-21 | 1990-08-21 | The United States Of America As Represented By The Secretary Of The Air Force | Field separable ordnance stepover bracket |
| US5225816A (en) * | 1991-08-12 | 1993-07-06 | Motorola, Inc. | Electrical connector with display |
| US5667398A (en) * | 1995-09-13 | 1997-09-16 | General Motors Corporation | Modular connection system |
| JP3236775B2 (en) | 1996-03-18 | 2001-12-10 | 株式会社オートネットワーク技術研究所 | Connector connection structure |
| GB9715378D0 (en) | 1997-07-23 | 1997-09-24 | Tec Electrical Components Limi | Connector assemblies |
| US6361357B1 (en) * | 2000-04-13 | 2002-03-26 | 3Com Corporation | Remotely illuminated electronic connector for improving viewing of status indicators |
| US6752655B1 (en) * | 2000-05-12 | 2004-06-22 | Textron Automotive Company Inc. | Method and structure for fixing a locking connector to a vehicle member |
| DE20016889U1 (en) * | 2000-09-29 | 2000-12-21 | Schwarz Verbindungs-Systeme GmbH, 75382 Althengstett | Plate unit adjustable in the X / Y direction for wall cladding elements or the like which can be detachably attached by means of spring clips. |
| JP3994838B2 (en) | 2002-09-24 | 2007-10-24 | 住友電装株式会社 | Connector assembly structure |
-
2006
- 2006-03-17 DE DE102006012730A patent/DE102006012730B3/en not_active Expired - Fee Related
-
2007
- 2007-03-16 RU RU2008141137/07A patent/RU2432651C2/en not_active IP Right Cessation
- 2007-03-16 WO PCT/EP2007/052500 patent/WO2007107511A1/en active Application Filing
- 2007-03-16 CN CN2007800095781A patent/CN101405918B/en not_active Expired - Fee Related
- 2007-03-16 CA CA002644159A patent/CA2644159A1/en not_active Abandoned
- 2007-03-16 EP EP07726980.1A patent/EP2005533B8/en not_active Not-in-force
- 2007-03-16 JP JP2008558830A patent/JP2009530150A/en active Pending
- 2007-03-16 BR BRPI0708845-0A patent/BRPI0708845A2/en not_active IP Right Cessation
- 2007-03-16 US US12/281,524 patent/US8167624B2/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| RU2432651C2 (en) | 2011-10-27 |
| CN101405918A (en) | 2009-04-08 |
| EP2005533B8 (en) | 2016-12-28 |
| CA2644159A1 (en) | 2007-09-27 |
| JP2009530150A (en) | 2009-08-27 |
| US8167624B2 (en) | 2012-05-01 |
| RU2008141137A (en) | 2010-04-27 |
| DE102006012730B3 (en) | 2007-11-08 |
| WO2007107511A1 (en) | 2007-09-27 |
| US20090221154A1 (en) | 2009-09-03 |
| BRPI0708845A2 (en) | 2011-06-14 |
| EP2005533A1 (en) | 2008-12-24 |
| EP2005533B1 (en) | 2016-11-16 |
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